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High-power xenon ion thrustersSteady state performance characteristics for a 25-cm diameter laboratory-model xenon ion thruster operating over the power range from 1.8 to 6.8 kW are described. Performance data are also presented for a similar 30-cm diameter thruster operated over the 1.4 to 11.1 kW power range. For each of the two thrusters, thermal characteristics, discharge-chamber performance data, overall thruster performance data, and beam-current density profiles are presented. A high level of performance and stability over a wide range of input power is demonstrated for the two thrusters. It is concluded that there appears to be no technological obstacles in the way of developing flight-design thrusters that operate in the 5- to 10-kW power range for near-term applications to orbit raising.
Document ID
19900055481
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Beattie, J. R.
(Hughes Research Labs. Malibu, CA, United States)
Matossian, J. N.
(Hughes Research Laboratories Malibu, CA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2540
Accession Number
90A42536
Funding Number(s)
CONTRACT_GRANT: NAS3-25553
Distribution Limits
Public
Copyright
Other

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